CN212779853U - Short axial static pressure detecting tube for measuring core flow Mach number of transonic wind tunnel test section - Google Patents
Short axial static pressure detecting tube for measuring core flow Mach number of transonic wind tunnel test section Download PDFInfo
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- CN212779853U CN212779853U CN202022102080.5U CN202022102080U CN212779853U CN 212779853 U CN212779853 U CN 212779853U CN 202022102080 U CN202022102080 U CN 202022102080U CN 212779853 U CN212779853 U CN 212779853U
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Abstract
The utility model discloses a measure minor axis static pressure detecting tube of transonic wind tunnel test section core flow mach number. The short axial static pressure detecting tube is a long and straight round tube and is arranged on a horizontal axis of a transonic wind tunnel test section; the head of the short axial static pressure detection pipe is in a conical revolution body, a bus of the conical revolution body is an arc curve, and a sharp point of the head of the short axial static pressure detection pipe is in a direction facing to the core flow of the test section of the transonic wind tunnel and extends into the molded surface of the sonic nozzle in front of the throat; the middle section of the short axial static pressure detection tube is a cylindrical section; the rear section of the short axial static pressure detection tube is a cylindrical measurement section, is positioned in a core flow field of a transonic wind tunnel test section, is provided with a series of linearly distributed static pressure measurement points along the axial direction of the transonic wind tunnel, and the tail end of the short axial static pressure detection tube is fixed on a wind tunnel bent knife mechanism of the test section. The short axial static pressure detecting tube is high in measuring accuracy, convenient and fast to install, capable of reducing test preparation workload and reducing interference influence of a hole body tool.
Description
Technical Field
The utility model belongs to high-speed wind tunnel test field, concretely relates to measure minor axis to static pressure detecting tube of transonic wind tunnel test section core stream mach number.
Background
In order to meet the requirement of more refinement of modern advanced aircraft development and realize the aim of development of wind tunnel tests towards simulation reality and measurement refinement, higher requirements are provided for the flow field quality of a high-performance transonic wind tunnel. In order to inspect the quality of the flow field of the wind tunnel and determine whether the wind tunnel meets the development requirement of an aircraft, the flow field calibration and measurement work needs to be carried out regularly. The items of flow field calibration mainly comprise a velocity field, a direction field, transonic speed ventilation wall wave-absorbing characteristics, a cavity wall boundary layer, airflow noise, turbulence, low-frequency pulsation of airflow and the like. Wherein the velocity field is a necessary calibration item. In general speed field calibration, static pressure measured by a long axial static pressure detecting tube and total wind tunnel pressure are usually adopted to calculate and obtain a central line of a test section, namely Mach number on a core stream, and finally, the axial distribution characteristic of the Mach number of the core stream and the correction relation between the Mach number of a wind tunnel test and the Mach number of a parking room are obtained.
The tail part of the long axial static pressure detection pipe is fixedly arranged on the wind tunnel bent knife mechanism and is positioned on the central line of the test section, and the head part of the long axial static pressure detection pipe needs to penetrate through the test section and the spray pipe section and extend to the contraction section, and the length of the long axial static pressure detection pipe can reach tens of meters in a large transonic wind tunnel. In order to ensure the coincidence of the central line of the axial static pressure detecting tube and the axis of the wind tunnel, the strength and the rigidity of the axial static pressure detecting tube and the safety of the wind tunnel test, the axial static pressure detecting tube needs to be tensioned and fixed by steel ropes at a plurality of positions of a spray pipe or a test section, the tooling is complex and certain influence is caused on the flow field of the test section. Meanwhile, a large number of holes and grooves are required to be formed in the spraying pipe section and the test section due to the need of pulling and fixing the tool, and the structure of the hole body is also adversely affected.
Aiming at the defects of a long axial static pressure detecting tube, the short axial static pressure detecting tube capable of being used for measuring the core flow Mach number of a transonic wind tunnel test section is designed.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem that a measure short axial static pressure detecting tube of transonic wind tunnel test section core flow mach number is provided.
The short axial static pressure detecting tube for measuring the core flow Mach number of the transonic wind tunnel test section is a long and straight round tube and is arranged on a horizontal axis of the transonic wind tunnel test section; the head of the short axial static pressure detection pipe is in a conical revolution body, a bus of the conical revolution body is an arc curve, and a sharp point of the head of the short axial static pressure detection pipe is in a direction facing to the core flow of the test section of the transonic wind tunnel and extends into the molded surface of the sonic nozzle in front of the throat; the middle section of the short axial static pressure detection tube is a cylindrical section; the rear section of the short axial static pressure detection tube is a cylindrical measurement section, is positioned in a core flow field of a transonic wind tunnel test section, is provided with a series of linearly distributed static pressure measurement points along the axial direction of the transonic wind tunnel, and the tail end of the short axial static pressure detection tube is fixed on a wind tunnel bent knife mechanism of the test section.
Further, the length of the conical rotating body is L, the diameter of the bottom of the conical rotating body is D, the length-to-fineness ratio of the head of the conical rotating body is F ═ L/D, and F is (7-8): 1.
further, the latitude circle of the conical rotating body is taken as a reference plane, the upper vertex of the latitude circle facing the core flow of the transonic wind tunnel test section in the clockwise direction is 0 degree, the right vertex of the latitude circle is 90 degrees, the lower vertex of the latitude circle is 180 degrees, and the left vertex of the latitude circle is 270 degrees, and the static pressure measuring points are arranged on the straight lines at the positions of 0 degree and 180 degrees of the cylindrical measurement section or the straight lines at the positions of 0 degree, 90 degree, 180 degree and 270 degree of the cylindrical measurement section.
Furthermore, the short axial static pressure detection tube is made of hard aluminum or stainless steel.
The utility model discloses a measure minor axis static pressure detecting tube of transonic wind tunnel test section core flow mach number is fixed in the test section central line through wind-tunnel bent knife mechanism on, before the detecting nose portion is located the velocity of sound spray pipe throat, takes the method that conventional flow field school was surveyed and is acquireed test data, can realize the comparatively accurate measurement of transonic wind tunnel subspan hyper core flow mach number. The length of the short axial static pressure detection tube is greatly reduced relative to the length of the long axial static pressure detection tube, the installation is more convenient and faster, and the workload during the test preparation period is greatly reduced. Moreover, the bracing wire support can be reduced or not used according to actual conditions, and the interference influence of the hole body tool can be effectively reduced.
To sum up, the utility model discloses a measure short axial static pressure detecting tube of transonic wind tunnel test section core flow mach number and measure the precision height, simple to operate is swift, has reduced experimental preparation work load, has reduced the influence of hole body frock interference.
Drawings
FIG. 1 is a schematic view of the wind tunnel installation of the short axial static pressure probe tube for measuring the Mach number of the core flow of the transonic wind tunnel test section of the utility model;
fig. 2 is the utility model discloses a measure short axial static pressure of transonic wind tunnel test section core flow mach number and survey the schematic diagram of nose.
In the figure, 1 is a short axial static pressure detecting tube 2, a transonic wind tunnel test section 3, a wind tunnel bent knife mechanism 4, a sonic nozzle molded surface 5, a static pressure measuring point 6, a short axial static pressure detecting tube head 7 and a throat.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings and examples.
As shown in fig. 1, the short axial static pressure probe tube 1 for measuring the core flow mach number of the transonic wind tunnel test section of the utility model is a long and straight round tube and is installed on the horizontal axis of the transonic wind tunnel test section 2; the shape of the short axial static pressure detecting pipe head 6 is a conical revolution body, the generatrix of the conical revolution body is an arc curve, and the sharp point of the short axial static pressure detecting pipe head 6 is faced to the core flow of the transonic wind tunnel test section and extends into the sound velocity spray pipe molded surface 4 in front of the throat 7; the middle section of the short axial static pressure detection tube 1 is a cylindrical section; the rear section of the short axial static pressure detecting tube 1 is a cylindrical measuring section, is positioned in a core flow field of a transonic wind tunnel test section, is provided with a series of linearly distributed static pressure measuring points 5 along the axial direction of the transonic wind tunnel, and the tail end of the short axial static pressure detecting tube 1 is fixed on a wind tunnel curved knife mechanism 3 of the test section;
further, as shown in fig. 2, the length of the tapered revolution body is L, the diameter of the bottom is D, the length-to-fineness ratio of the head is F ═ L/D, and F is (7-8): 1.
further, with the latitude circle of the conical revolution body as a reference plane, the upper vertex of the latitude circle facing the clockwise direction of the core flow of the transonic wind tunnel test section is 0 degree, the right vertex of the latitude circle is 90 degrees, the lower vertex of the latitude circle is 180 degrees, and the left vertex of the latitude circle is 270 degrees, and the static pressure measuring points 5 are arranged on the straight lines at the positions of 0 degree and 180 degree of the cylindrical measurement section or the straight lines at the positions of 0 degree, 90 degree, 180 degree and 270 degree of the cylindrical measurement section.
Furthermore, the short axial static pressure detecting tube 1 is made of hard aluminum or stainless steel.
Example 1
The length of the short axial static pressure probe tube 1 of the present embodiment is 2.5m, and the head slenderness ratio is F-8.
The specific working process of this embodiment is as follows:
1. mounting the short axial static pressure detection tube 1 on a wind tunnel curved knife mechanism 3 of a transonic wind tunnel test section 2, and adjusting the attack angle of the wind tunnel curved knife mechanism 3 to 0 degree;
2. opening a transonic wind tunnel;
3. collecting static pressure data of the static pressure measuring point 5 by adopting a pressure scanning valve, and closing the transonic wind tunnel;
4. and calculating to obtain the core flow Mach number of the transonic wind tunnel.
Claims (4)
1. A short axial static pressure detecting tube for measuring the Mach number of a core flow of a transonic wind tunnel test section is characterized in that the short axial static pressure detecting tube (1) is a long and straight round tube and is installed on a horizontal axis of the transonic wind tunnel test section (2); the shape of the short axial static pressure detection pipe head (6) is a conical revolution body, the generatrix of the conical revolution body is an arc curve, and the sharp point of the short axial static pressure detection pipe head (6) faces the core flow of the transonic wind tunnel test section and extends into the sonic nozzle molded surface (4) in front of the throat (7); the middle section of the short axial static pressure detection tube (1) is a cylindrical section; the rear section of the short axial static pressure detection pipe (1) is a cylindrical measurement section, is positioned in a core flow field of a transonic wind tunnel test section, is provided with a series of linearly distributed static pressure measurement points (5) along the axial direction of the transonic wind tunnel, and the tail end of the short axial static pressure detection pipe (1) is fixed on a wind tunnel bent knife mechanism (3) of the test section.
2. The short axial static pressure probe tube for measuring the core flow Mach number of the transonic wind tunnel test section according to claim 1, wherein the length of the conical rotating body is L, the diameter of the bottom of the conical rotating body is D, the length-to-fineness ratio of the head is F-L/D, and F is (7-8): 1.
3. the short-axis static pressure probe tube for measuring the core flow mach number of the transonic wind tunnel test section according to claim 1, characterized in that a latitude circle of a conical rotating body is taken as a reference surface, an upper vertex of the latitude circle facing to the clockwise direction of the transonic wind tunnel test section is 0 degrees, a right vertex of the latitude circle is 90 degrees, a lower vertex of the latitude circle is 180 degrees, and a left vertex of the latitude circle is 270 degrees, and the static pressure measuring points (5) are arranged on a straight line at 0 degrees and 180 degrees of a cylindrical measurement section or on a straight line at 0 degrees, 90 degrees, 180 degrees and 270 degrees of the cylindrical measurement section.
4. The short axial static pressure detecting tube for measuring the core flow Mach number of the transonic wind tunnel test section according to claim 1, characterized in that the short axial static pressure detecting tube (1) is made of duralumin or stainless steel.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202022102080.5U CN212779853U (en) | 2020-09-23 | 2020-09-23 | Short axial static pressure detecting tube for measuring core flow Mach number of transonic wind tunnel test section |
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| CN202022102080.5U CN212779853U (en) | 2020-09-23 | 2020-09-23 | Short axial static pressure detecting tube for measuring core flow Mach number of transonic wind tunnel test section |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114608792A (en) * | 2022-05-10 | 2022-06-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for measuring uniform region of sub-transonic jet flow field of high-speed jet wind tunnel by short-shaft probe |
| CN116499699A (en) * | 2023-06-29 | 2023-07-28 | 中国航空工业集团公司沈阳空气动力研究所 | Continuous wind tunnel pressure measurement test data monitoring and correcting method |
| CN116735142A (en) * | 2023-08-14 | 2023-09-12 | 中国航空工业集团公司沈阳空气动力研究所 | Background noise suppression method for continuous transonic wind tunnel ventilation wall test section |
| CN117129179A (en) * | 2023-10-26 | 2023-11-28 | 中国航空工业集团公司沈阳空气动力研究所 | Mach number correction method for double-support test under continuous wind tunnel wing |
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2020
- 2020-09-23 CN CN202022102080.5U patent/CN212779853U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114608792A (en) * | 2022-05-10 | 2022-06-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for measuring uniform region of sub-transonic jet flow field of high-speed jet wind tunnel by short-shaft probe |
| CN114608792B (en) * | 2022-05-10 | 2022-07-15 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for measuring uniform region of sub-transonic jet flow field of high-speed jet wind tunnel by short-shaft probe |
| CN116499699A (en) * | 2023-06-29 | 2023-07-28 | 中国航空工业集团公司沈阳空气动力研究所 | Continuous wind tunnel pressure measurement test data monitoring and correcting method |
| CN116499699B (en) * | 2023-06-29 | 2023-08-22 | 中国航空工业集团公司沈阳空气动力研究所 | Continuous wind tunnel pressure measurement test data monitoring and correcting method |
| CN116735142A (en) * | 2023-08-14 | 2023-09-12 | 中国航空工业集团公司沈阳空气动力研究所 | Background noise suppression method for continuous transonic wind tunnel ventilation wall test section |
| CN116735142B (en) * | 2023-08-14 | 2023-10-20 | 中国航空工业集团公司沈阳空气动力研究所 | Background noise suppression method for continuous transonic wind tunnel ventilation wall test section |
| CN117129179A (en) * | 2023-10-26 | 2023-11-28 | 中国航空工业集团公司沈阳空气动力研究所 | Mach number correction method for double-support test under continuous wind tunnel wing |
| CN117129179B (en) * | 2023-10-26 | 2023-12-26 | 中国航空工业集团公司沈阳空气动力研究所 | Mach number correction method for double-support test under continuous wind tunnel wing |
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